Monopropellant

Fig. 1. The postulated flame stmcture for an AP composite propellant, showing A, the primary flame, where gases are from AP decomposition and fuel pyrolysis, the temperature is presumably the propellant flame temperature, and heat transfer is three-dimensional followed by B, the final diffusion flame, where gases are O2 from the AP flame reacting with products from fuel pyrolysis, the temperature is the propellant flame temperature, and heat transfer is three-dimensional and C, the AP monopropellant flame where gases are products from the AP surface decomposition, the temperature is the adiabatic flame temperature for pure AP, and heat transfer is approximately one-dimensional. AP = ammonium perchlorate.

RocketPropella.nts, Liquid propellants have long been used to obtain maximum controUabiUty of rocket performance and, where required, maximum impulse. Three classes of rocket monopropellants exist that differ ia the chemical reactions that release energy (/) those consisting of, eg, hydrogen peroxide, ethylene oxide, C2H4O and nitroethane, CH2CH2NO2 that can undergo internal oxidation—reduction reactions (2) those... 

H. H. Voge and co-workers. Development of Catalystsfor Monopropellant Decomposition ofHydra ne, Final Report 3-13947, Contract NAS 7-97, Shell Development Co., Emeryville, Calif., Apr.—Dec. 1964. 

The following Add ft Pjsfs are of limited distribution 1) G.A. Yanyecic, Decomposition Characteristics of Nitrate Ester Monopropellants , Rept No TM-705. 9161-03, Contract NOW-65-0123, Penn State Univ, Univ Park (1968) 2) R.K. Lund, Encapsulated Liquid... 

The redox salt which decomposes at 100°C, evolving nitrogen and oxygen [1] is overall an oxidant but has been used as a reducant in actinide processing [2], It has been used recently as a missile monopropellant [3], and also as an oxidant, with its isopropyl derivative as the fuel [4],... 

Feath, G. M., "High-Pressure Liquid-Monopropellant Strand Combustion," Combustion and Flame, 18 (1972). 

Cachia, G. P. und Withebread, E. G. The Initiation of Explosives by Shock, Proc. Roy. Soc. A 246, 268-273 (1958). Card-Gap Test for Shock Sensitivity of Liquid Monopropellant, Test Nr. 1, Recommended by the JANAF Panel on Liquid Monopropellant Test Methods, March 1960 Amster, A. B., Noonan, E. C. und Bryan, G. J. Solid Propellant Detonability, ARS-Journal 30, 960-964 (1960)... 

Liquid hydrazine (N2H4) decomposes exothermically in a monopropellant rocket operating at 100 atm chamber pressure. The products formed in the chamber are N2, H2, and ammonia (NH3) according to the irreversible reaction... 

Propellant chemists have proposed a new high energy liquid oxidizer, penta-oxygen 05, which is also a monopropellant. Calculate the monopropellant decomposition temperature at a chamber pressure of 10 atm if it assumed the only products are O atoms and 02 molecules. The heat of formation of the new oxidizer is estimated to be very high, +1025 kJ/mol. Obviously, the amounts of 02 and O must be calculated for one mole of 05 decomposing. The 05 enters the system at 298 K. Hint The answer will lie somewhere between 4000 and 5000 K. 

An ethylene oxide monopropellant rocket motor is considered part of a ram rocket power plant in which the turbulent exhaust of the rocket reacts with induced air in an afterburner. The exit area of the rocket motor is 8 cm2. After testing it is found that the afterburner length must be reduced by 42.3%. What size must the exit port of the new rocket be to accomplish this reduction with the same afterburner combustion efficiency The new rocket would operate at the same chamber pressure and area ratio. How many of the new rockets would be required to maintain the same level of thrust as the original power plant ... 

The data presented in Table El are for fuel gases and vapors and are taken almost exclusively from Zabetakis. [IJS Bur. Mines Bull. 627 (1965)]. The conditions are for the fuel-air mixture at 25°C and 1 atm unless otherwise specified. As noted in the text, most fuels have a rich limit at approximately = 3.3 and a lean limit at approximately = 0.5. The fuels which vary most from the rich limit are those that are either very tightly bound as ammonia is or which can decompose as hydrazine or any monopropellant does. Additional sources of flammability limit data can be found in the Ignition Handbook by Babrauskas (Fire Science Publishers, Issaquah, WA, 2003) and from Kuchta [1/5 Bur. Mines Bull. 680 (1985)]. 

N-propyl nitrate org chem C3H7NO3 A white to straw-colored liquid with a boiling range of I04-I27°C used as a monopropellant rocket fuel. en pro-pal nT.trat) propylparaben orgchem C,oH,203 Colorless crystals or white powder with a melting point of 9 j-98°C soluble in acetone, ether, and alcohol used in medicine and as a food preservative and fungicide.. pro pal par-a-ban ... 

Uses Laboratory reagent for detecting double bonds in organic compounds oxidizer in rocket propellants monopropellant increase octane rating for diesel fuel. 

Liau, Y.-C., and V. Yang. 1995. Analysis of RDX monopropellant combustion with two-phase surface reactions. J. Propulsion Power 11 729-39. 

Nitramine composite propellants composed of HMX or RDX particles and polymeric materials offer the advantages of low flame temperature and low molecular mass combustion products, as well as reduced infrared emissions. The reduced infrared emissions result from the elimination of COj and H2O from the combustion products. To formulate these composite propellants, crystalline nitramine monopropellants such as HMX or RDX are mixed with a polymeric binder. Since both HMX and RDX are stoichiometrically balanced, the polymeric binder acts as a coolant, producing low-temperature, fuel-rich combustion products. This is in contrast to AP composite propellants, in which the binder surrounding the AP particles acts as a fuel to produce high-temperature combustion products. 

When nitramine particles such as HMX or RDX particles are mixed with a doublebase propellant, nitramine composite-modified double-base propellants are formulated. Since HMX and RDX are stoichiometrically balanced materials, the use of these nitramine particles leads to a somewhat different mode of combustion as compared to AP-CMDB propellants. Since each nitramine particle can burn independently of the base matrix at the burning surface, a monopropellant flamelet is formed in the gas phase from each particle. The monopropellant flamelet diffuses into the reactive gas of the base matrix above the burning surface and a homogeneously mixed gas is formed. 

The ballistic properties of ADN, HNF, and HNIW as monopropellants and as oxidizers in composite propellants have been extensively studied.P2-351 Since ADN, HNF, and HNIW particles produce excess oxygen among their combustion products, these particles are used as oxidizer crystals in composite propellants. The pressure exponents of crystalline ADN and HNIW particles are both approximately about the same value as those for HMX and RDX when they are burned as pressed pellets. However, the pressure exponent of HNF is 0.85-0.95,135] higher than those of the other energetic crystalline oxidizers. 

Nachbar, "Deflagration Limits in the Steady Linear Burning of a Monopropellant With Application of Ammonium Perchlorate ,... 

M.A. Cook et al, JApplPhys 30, 1579-84(1959) (Instrumented Card-Gap or SPHF-Plate Test) 23) Baum, Stanyukovich Shekhter (1959). 754-71 (Deton by influence thru air) 771-78 (Deton by influence thru condensed media) 778-81 (Safe distances for propagation of deton betw some expl chges used in Rus coal mines) 23a) Liquid Propellants Info Agency, Applied Physics Lab, Johns Hopkins Univ, "Liquid Propellants Test Methods, Test No 1, Card-Gap Test for Shock Sensitivity of Liquid Monopropellants (March i960)... 

The use of N2H4 as a hypergolic propellant fuel for rocket propulsion is discussed in detail in this Vol under Hypergolic Propellants. It has also been used extensively as a monopropellant fuel or in combination with hydrazine nitrate and/or water as a thruster for maneuvering space vehicles (Ref 31)... 

Schmitz W.W. Wilson, Long Life Monopropellant Hydrazine Engine Development Program, Final Rept, Rocket Research, RRC-71-R-257 (Sept 1951) (Available NTIS-AD-731287) 14) Ullmann, 6, 206, Encyklopadie der Technischen Chemie (1951) 14a) Ch.C. 

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